Segmented Exhaust Manifold Gas Seals

ABSTRACT

System and methods for preventing leakage of exhaust gasses in the segmented manifold of an engine system are disclosed. In an aspect, an assembly includes a first manifold, a flange, and a first carrier and a second carrier having recessed portions configured to accommodate compressions rings to deliver a sealing force.

TECHNICAL FIELD

The present disclosure is related to a seal in an engine exhaust system and more specifically to a seal for a segmented exhaust manifold assembly.

BACKGROUND

An internal combustion engine can employ an exhaust manifold to direct combustion products away from the engine's combustion chambers. These combustion products, making up exhaust gases, are instead channeled out to the ambient environment. In some instances, the engine's exhaust manifold may be formed as a single unitary body featuring a number of exhaust inlets interconnected with respective cylinders in fluid communication with corresponding combustion chambers.

Also common in combustion engine systems are segmented exhaust manifold assemblies. These manifold assemblies include a number of individual manifold segments, each segment typically connected to an associated cylinder of the internal combustion engine to receive the combustion products therefrom. The manifold segments may be joined via slip joints and/or bolts extending through flanges of adjacent manifold segments. The manifold segments may be configured to accommodate varying distances between the respective segments allowing for thermal expansion and contraction during periods of operation and inactivity of the internal combustion engine.

One problem which may arise in internal combustion engines utilizing a segmented manifold assembly is that the bolted connection and generally planar surfaces between the two flanges, or between the male and female manifold portions of the slip joint, may not provide a sufficient seal thereby allowing exhaust gases to leak from the manifold assembly. Gaskets or sealants may also be used in a flanged connection between the exhaust connector and manifold segments. Conventional techniques of compensation for thermal expansion have also involved the use of seal rings. As an example, to compensate for thermal expansion during operation of the internal combustion engine and thermal contraction after operation is complete in a segmented exhaust manifold, a seal may be used in combination with the flanged connection.

Still, conventional segmented exhaust manifold assemblies can experience leakage whether flanged or slip jointed connections are employed. For example, seal rings known in the art have a tendency to fatigue and leak over time as a result of the engine's high temperature and high motion environment.

U.S. Pat. No. 4,641,861 provides a seal having a flexible joint, especially adapted for pipes in an exhaust system of an engine is disclosed. The patent discloses a locking ring is disposed over a flared end of the first pipe and a stop flange and a slidable locking flange are both provided on the second pipe with a wave spring disposed between them. A sealing ring having a spherical surface is positioned by a sealing socket in the flared end of the first pipe. Bayonet coupling members on the locking ring and on the locking flange, respectively, are provided to assemble the joint by pressing the locking ring and the locking flange together against the resistance of the wave spring and rotating them relative to one another to engage the bayonet coupling. The active seal created however remains subject to leaking at the connections joining the individual pipes.

These and other shortcomings of the prior art are addressed by the present disclosure.

SUMMARY OF THE DISCLOSURE

In an aspect, an assembly includes a first manifold segment having a first fluid conduit formed therein and having a flange at a first end of the first manifold segment, a first carrier disposed adjacent the flange, the first carrier defining at least a portion of a first internal surface, a first recessed portion disposed adjacent the first carrier; a second manifold segment having a second fluid conduit formed therein, the second manifold segment disposed adjacent the first internal surface, and a compression ring disposed adjacent the first recessed portion.

In an aspect, a first manifold segment having a first fluid conduit formed therein and having a flange disposed at a first end of the first manifold segment; a first carrier coupled to the flange, wherein the first carrier defines at least a portion of a first recess and a portion of a second recess; a first compression ring disposed adjacent the first recess; a second compression ring disposed adjacent the second recess, wherein the second compression ring has a concave curvature or concave polygonal cross-section, wherein an interior angle is oriented towards the first compression ring; and a second manifold segment having a second fluid conduit formed therein, the second manifold disposed adjacent an internal surface of the first carrier, wherein the first and second compression rings provide sealing engagement between the second manifold and the first carrier.

In an aspect, a first manifold segment having a first fluid conduit formed therein and having a flange disposed at a first end of the first manifold segment; a first carrier coupled to the flange; a first recessed portion formed in the first end of the first carrier; a spring element disposed adjacent the first recessed portion; a compression ring disposed adjacent the spring element; and a second manifold segment having a second fluid conduit formed therein, the second manifold segment disposed adjacent an internal surface of the first carrier, wherein the spring biases the compression ring to provide sealing engagement between the second manifold segment and the first carrier.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic diagram of an internal combustion engine with a segmented exhaust manifold assembly in accordance with aspects of the present disclosure.

FIG. 2 is a schematic diagram of a portion of a segmented exhaust manifold assembly in accordance with aspects of the present disclosure.

FIG. 3 is a cross-sectional view of the segmented exhaust manifold assembly of FIG. 2 in accordance with aspects of the present disclosure.

FIG. 4 is an exploded view of a first compression ring in accordance with aspects of the present disclosure.

FIG. 5 is a cross-sectional view of a segmented exhaust manifold assembly in accordance with aspects of the present disclosure.

FIG. 6 is a cross-sectional view of a segmented exhaust manifold assembly in accordance with aspects of the present disclosure.

FIG. 7 is a cross-sectional view of a segmented exhaust manifold assembly in accordance with aspects of the present disclosure.

DETAILED DESCRIPTION

The present disclosure is directed towards improving a slip fit joint. In one aspect of the present disclosure, a slip-fit assembly for a segmented exhaust manifold may be configured to deliver a radial and axial force to seal the connected manifold segments to prevent exhaust leakage in the manifold assembly. In several embodiments further described in more detail below, this may be accomplished by incorporating compression rings and recessed portions into one or more carriers coupled to a flange of a manifold segment.

FIG. 1 illustrates an internal combustion engine 100 having an exhaust manifold assembly 102. The exhaust manifold assembly 102 includes a plurality of manifold segments 104, for example, a first manifold segment 104A and a second manifold segment 104B in fluid communication with each other. As shown in FIG. 1, each of the manifold segments 104 may be in fluid communication with respective combustion cylinders 106 of the internal combustion engine 100. The combustion cylinders 106 may form a cylinder bank 108 from which the manifold segments 104 receive an exhaust gas combustion product. The manifold segments 104 and the cylinder bank 108 may be in fluid communication via an exhaust passage (not shown). As shown, a cylinder head 110 may be secured to the engine 100 adjacent the cylinder bank 108 of combustion cylinders 106.

As an illustrative example, as pressure builds and temperatures rise in the combustion engine 100, leakage may occur between the manifold segments 104 where a conventional slip fit joints may not provide an adequate seal. The present disclosure relates to a slip-fit assembly 112 configured to minimize and/or prevent this seepage of exhaust gases from the connected manifold segments 104 in the exhaust manifold assembly 102.

Referring to FIG. 2, the slip-fit assembly 112 fluidly connects two manifold segments, e.g., 104A and 104B and may include a flange 214, a first carrier 216, and a second carrier 218. In one aspect, the flange 214 may be disposed at a first end 222 of the first manifold segment 104A. The first carrier 216 may be coupled to the flange 214 of the first manifold segment 104A by one or more coupling mechanisms 220 such as bolt and nut mechanisms. The first carrier 216 may be spaced from the flange 214, for example, such that the second carrier 218 may be disposed between the first carrier 216 and the flange 214 of the first manifold segment 104A. As such, the coupling mechanisms 220 may couple both the first and second carriers 216, 218 to the flange 214, whereby the second carrier 218 is positioned between the first carrier 216 and the flange 214 and the second carrier 218 is subject to a compression force provided by the coupling mechanisms 220 and the first carrier 216.

Referring to FIG. 3, the first carrier 216 and the second carrier 218 may include a through hole and may collectively define a first internal surface 332 along an internal periphery of each of the first and second carriers 216, 218. As an example, the first internal surface 332 may be sized to have a diameter configured to receive at least a portion of one of the manifold segments 104 such as the second manifold segment 104B. As such, the first and second carriers 216, 218 may receive the second manifold segment 104B and allow a fluid conduit 324 of the first manifold segment 104A to be in fluid communication with a fluid conduit 338 of the second manifold segment 104B.

In certain aspects, the second manifold segment 104B may have a first end 336 that is disposed substantially at a 90 degree (°) angle to the first internal surface 332. As used herein, the term “substantially at a 90° angle” can mean that the deviation as an angle measured relative to the normal first internal surface 332 is less than or equal to 10%. As the second manifold segment 104B is disposed adjacent the first internal surface 332, a gap 334 may be defined between by the first end 336 and the flange 214.

In some aspects, the first manifold segment 104A, the second manifold segment 104B, the first carrier 216, and the second carrier 218 may be cast from the same material or materials having a same or similar thermal profile. A same or similar thermal profile between the materials may ensure that the first manifold segment 104A, the second manifold segment 104B, the first carrier 216, and the second carrier 218 exhibit comparable thermal expansion and contraction properties. At elevated temperature and pressure during operation of the engine 100, comparable thermal expansion and contraction properties can facilitate the generation of a sealing force in axial and radial directions within the slip fit assembly 112. In various aspects, one or more compression rings may be included in the slip fit assembly 112 to provide sealing engagement between the manifold segments 104.

A first recessed portion 340 may be disposed in a first end 326 of the first carrier 216. The first recessed portion 340 may be disposed in the first end 326 of the first carrier 216 abutting a first end 330 of the second carrier 218 opposite a second end 328 of the first carrier 216. The first recessed portion 340 may be disposed adjacent to the first internal surface 332. The first recessed portion 340 is configured such that the first carrier 216 may accommodate a compression ring 342. As an example, when the second manifold segment 104B is disposed adjacent the first internal surface 332 so that the second manifold segment 104B is positioned within the carriers 216, 218, the compression ring 342 may be disposed around an outer periphery of the second manifold segment 104B and may be in sealing engagement therewith. As such, the compression ring 342, configured with the first carrier 216 and second carrier 218, may deliver a radial, elastic restoring force between the first carrier 216 and second manifold segment 104B disposed therein and deliver an axial, elastic restoring force between the first and second carriers 216, 218.

As presented in FIGS. 3, 5, 6, and 7, the recessed portions included in embodiments of the present disclosure may have a have a particular shape or geometry. In one example, the first recessed portion 340 may be annular and may have a generally rectangular cross-section. Alternative shapes, such as round or triangular or polygonal, may be the cross-sectional geometry of the recessed portions in the various embodiments disclosed herein.

Referring to FIGS. 3 and 4, the compression ring 342 may include an outer shell 444 having a mesh core 446 or interior. According to one aspect of the disclosure, the outer shell 444 may include a split housing having a first shell portion 444A and a second shell portion 444B. The first and second shell portions 444A, 444B may be coupled together to secure the mesh core 446 therebetween. In certain embodiments, first and second shell portions 444A, 444B may be moveable coupled to each other such that a restoring force of the compressed mesh core 446 may provide radial and axial forces on the first and second shell portions 444A, 444B. The mesh core 446 may be a compressible wire mesh ring. As an example, the shell 444 and the mesh core 446 may be composed of an appropriate high-temperature metal. As one skilled in the art might appreciate, a high-temperature metal may refer to a metal which exhibits resistance to deformation at high temperatures, such as above 450° F. These metals may include, but are not limited to, stainless steel or a nickel-chromium alloy.

FIG. 5 is a partial cross-sectional view of a slip fit assembly 500 similar to the slip fit assembly 112, except as described below. In one aspect, a first carrier 516 and a second carrier 518 may define a first internal surface 532. The first carrier 516 may have a first recessed portion 540 formed at a first end 526 of the first carrier 516 and the second carrier 518 may have a second recessed portion 552 formed at a first end 530 of the second carrier 518. The first end 526 of the first carrier 516 may abut the first end 530 of the second carrier 518. As such, the first recessed portion 540 and the second recessed portion 552 may accommodate a first compression ring 548.

In an aspect, the first compression ring 548 may include a mesh ring. As an example, the first compression ring 548 may include a woven mesh having a high temperature filler. The woven mesh of the first compression ring 548 may include coarse austenite (gamma-phase iron) stainless steel. The high temperature filler may include materials suitable for temperatures between 450° F. and 1200° F. As an example, the high temperature filler of the woven mesh may include graphite or mica. The woven mesh may exhibit dampening qualities during operation of the internal combustion engine. As an example, the woven mesh ring having high temperature filler can reduce the wear inside the assembly 500 and reduce motion.

In one aspect, the first recessed portion 540 and the second recessed portion 552 may have a certain shape and certain cross-sectional geometries. For example, the recessed portions 540, 548 may both be annular.

A third recessed portion 554 may be formed in a second end 528 of the first carrier 516, thereby defining a second internal surface 536. As such, the third recessed portion 554 is disposed adjacent the second manifold segment 104B, while the second manifold segment 104B is disposed adjacent the first and second carriers 516, 518. As noted herein, the third recessed portion 554 may have a particular shape or geometry. For example, the third recessed portion 554 may be annular and have a generally rectangular cross-section. The third recessed portion 554 may include a second compression ring 558 disposed therein.

In various aspects, the second compression ring may 558 be disposed adjacent a portion of the second internal surface 536. The second compression ring 558 may be configured to deliver a radial, elastic restoring force between the first carrier 216 and second manifold segment 104B disposed therein and to deliver an axial, elastic restoring force between the first and second carriers 216, 218 and ultimately throughout the assembly 500. The shape or geometry of the second compression ring 558 may contribute to the axial elastic restoring force delivered. In some aspects of the present disclosure, the second compression ring 558 may have a concave curvature or concave polygonal cross-section. For a concave curvature cross-sectional geometry of the second compression ring 558, the concave curvature may be oriented such that the curvature has its opening oriented toward the first compression ring 548 and so that the concave curvature abuts a portion of the second internal surface 536 formed by the third recessed portion 554. For a concave polygonal cross-section shape, the second compression ring 558 has an interior angle 560. The interior angle 560 may be oriented toward the first end 526 of the first carrier 516. In some aspects, the concave polygonal cross-section shape may be described as V-shaped, U-shaped, and the like. The concave geometry of the second compression ring 558, allows the second compression ring 558 to provide an axial elastic restoring force on a portion of the second internal surface 536. In various embodiments of the present disclosure, the geometry of the second compression ring 558 can exploit the pressure generated during operation of the internal combustion engine to force the second compression ring 558 open and thereby facilitate the seal of the slip fit assembly 500.

A fourth recessed portion 562 may be formed at the second end 528 of the first carrier 516. As noted herein, the fourth recessed portion may have a particular shape, such as for example, annular and having a generally rectangular cross-section. The fourth recessed portion 562 may define a third internal surface 564. To secure the second compression ring 558 within the third recessed portion 554 and to provide rigidity or stability within the assembly 500, the fourth recessed portion 562 may include an annular retainer 566 disposed therein. The annular retainer 566 may be disposed adjacent a portion of the third internal surface 564 formed by the fourth recessed portion 562 of the first carrier 516. In an aspect, the annular retainer may be disposed adjacent the second end 528 of the first carrier 516 such that the second compression ring 558 is disposed between the annular retainer 566 and a portion of the first carrier 516.

The assembly 600 as provided in FIG. 6 is similar to that of the assembly 112, 500 presented in FIGS. 1, 2, and 5, except that the embodiment includes altered configurations. FIG. 6 presents a full cross-sectional view of an embodiment of the assembly 600. The assembly 600 may include the flange 214, the first carrier 616, the second carrier 618, the one or more recessed portions 640, 652, and the compression ring 648.

As shown in FIG. 6, the flange 214, the second carrier 618, and the first carrier 616 may be joined by a coupling mechanism 620 such as a bolt. Further, the first carrier 616 may include a first recessed portion 640 and the second carrier 618 may include a second recessed portion 652 formed therein and configured to accommodate the compression ring 648 and a spring 668.

As noted above, the first recessed portion 640 and the second recessed portion 652 may have particular shapes. In one example, the recessed portions 640, 652 may both be annular. Regarding FIG. 6, the first recessed portion 640 may have a right triangular or a trapezoidal cross-sectional geometry to accommodate the compression ring 648. The compression ring 648 may have an irregular trapezoidal cross-section in that parallel sides of the trapezoidal cross-section are not the same length. The second recessed portion 652 may have a generally rectangular cross section to accommodate the spring 668.

The compression ring 648 may be disposed adjacent the second recessed portion 652 within the second carrier 618. The compression ring 648 may be similar to the first compression ring 548 as presented in FIG. 5. The compression ring 648 may similarly include a woven wire mesh having mica filler.

The spring 668 may be disposed adjacent the first recessed portion 640 of the first carrier 616. In this configuration, the spring 668 may be configured to bias the compression ring 648 against the second carrier 618 to achieve a radial and an axial seal throughout the assembly 600. The spring 668 may be a conical spring washer. The conical spring washer, also known as a wave washer or a Belleville washer, may deliver an elastic and force to the adjacent compression ring 648 thereby driving an axial force throughout the assembly 600. In a further aspect, the spring 668 may be a conical spring washer in series. The spring 668 may also be cast of a suitably high-temperature metal. Appropriate high-temperature metals may include stainless steel or a nickel-chromium alloy.

Referring to FIG. 6, the assembly 700 is similar to the assembly 600 of FIG. 6 except that the second manifold segment 704B has an altered configuration. The first carrier 716 and the second carrier 718 may define a first internal surface 732. The first carrier 716 may have a first recessed portion 740 formed at a first end 726 of the first carrier 716 and the second carrier 718 may have a second recessed portion 752 formed at a first end 730 of the second carrier 718. The first end 726 of the first carrier 716 may abut the first end 730 of the second carrier 718.

The second manifold segment 704B may define a second fluid conduit 738 and may include a shoulder 770 spaced from a second end 772 thereof. As such, the shoulder 770 may include a raised portion along the second manifold segment 704B and may abut a portion of the first internal surface 732 of the first carrier 716. The shoulder 770 may be situated such that a first compression ring 748 is disposed adjacent the shoulder 770 and adjacent the second recessed portion 752 within the first end 726 of the first carrier 716. The shoulder 770 may provide additional surface area to facilitate the sealing force in the assembly 700.

Also depicted in FIG. 7, the spring 768 may be disposed in the first recessed portion 740 within the first end 726 of the second carrier 716. The spring 768 may be disposed adjacent the first compression ring 748. As disclosed herein, the spring 768 may be a conical spring washer. As an example, the spring 768 may include a conical spring washer in series.

The first compression ring 748 may be disposed in the first recessed portion 740 within the first end 726 of the first carrier 716. The first compression ring 748 may be disposed adjacent the second recessed portion 752 within the second carrier 718. The first compression ring 748 may be similar to the first compression ring 548 as presented in FIG. 5. The first compression ring 748 may include a woven wire mesh having mica filler.

Further, the first compression ring 748 may include a polygonal cross-sectional geometry such, for example, as a pentagonal cross-section. However other shapes can be used. The polygonal cross-section may be formed in the first compression ring 748 comprising the woven mesh and mica filler as the first compression ring 748 is configured to fit within the first recessed portion 740 of the first carrier 716 and abuts the shoulder 770 as shown in FIG. 7.

In certain embodiments of the present disclosure, any portion of the first or second carriers 216, 218, 516, 518, 616, 618, 716, 718 can be integrated with the flange 214. In one example, the flange 214 may include the first carrier 216, 516, 616, 716. The configuration can provide additional stability throughout the assembly 112, 500, 600, 700 and facilitate sealing of the slip fit assembly 112, 500, 600, 700. In further examples, the assembly 112, 500, 600, 700 can comprise only a single carrier, the first carrier 216, 516, 616, 716 integrated with the flange 214. As such, the one or more recessed portions 540, 552, 554, 562, 640, 652, 740, 752 and one or more compression rings 342, 548, 558, 648, 748 may be disposed within the first carrier 216, 516, 616, 716.

In various embodiments, the first carrier 216, 516, 616, 716 and the second carrier 218, 518, 618, 718 may be congruent parts with the exception of the configuration of the one or more recessed portions 540, 552, 554, 562, 640, 652, 740, 752. More specifically, the first carrier 216, 516, 616, 716 and the second carrier 218, 518, 618, 718 may be configured such that the first carrier 216, 516, 616, 716 and the second carrier 218, 518, 618, 718 are symmetrical and/or interchangeable. The symmetry of the first carrier 216, 516, 616, 716 and the second carrier 218, 518, 618, 718 may allow for variation in the configuration of the assembly 112, 500, 600, 700 with respect to the positioning of the one or more recessed portions 540, 552, 554, 562, 640, 652, 740, 752. Further, the uniformity of the carriers 216, 218, 516, 518, 616, 618, 716, 718 allows for minimal design modification to achieve comparable sealing in an existing slip joint exhaust manifold assembly. Indeed, the assembly 112, 500, 600, 700 as disclosed herein may be readily adaptable as the geometries of the first carrier 216, 516, 616, 716 and the second carrier 218, 518, 618, 718 are similar and thus similarly apt for alternative configurations of the one or more recessed portions 540, 552, 554, 562, 640, 652, 740, 752.

In further aspects, the first manifold 104A, second manifold 104B and the flange 214 may have a coating deposited thereon. The coating can comprise a hardening agent configured harden the surface of the first manifold 104A, second manifold 104B and the flange 214 to limit, for example minimize, wear on the assembly 112, 500, 600, 700.

INDUSTRIAL APPLICABILITY

The assembly, and its respective embodiments presented herein, may be used with various internal combustion engines having a segmented exhaust manifold assembly. The various operational modes of the assembly, as described below, may cater to various operational requirements and/or malfunctions of the segmented exhaust manifold system. Indeed, the assembly of the present disclosure may be configured to provide a radial and axial seal at the junction of individual manifold segments across a spectrum of operational conditions. Such continued load application of the radial and axial seal force may prevent the leakage of exhaust gases from the segmented manifold assembly. Particularly, the assembly may be configured to deliver a positive, elastic force at manifold segment joints whether the engine is cooling or is engaged at elevated temperatures, from, for example, about 450° C. to about 750° C.

Several operational modes of the assembly will be described hereinafter with reference to FIGS. 1-7.

In a conventional internal combustion engine, such as the engine 100 depicted in FIG. 1, a nominal gap can be present in the conventional assembly along the first internal surface between the first and second carrier and the second manifold segment. The nominal gap provides a clearance to allow for thermal expansion of the assembly as the engine 100 rises in temperature. At operating temperatures as thermal expansion occurs, the first manifold segment and the second manifold segment can be in contact, ultimately wearing down the surfaces of second manifold assembly and diminishing the seal in the slip fit joint. Accordingly, in the conventional assembly, the elastic restoring force may be diminished.

FIG. 6 presents an operational mode of assembly 600. The flange 214 of the first manifold segment 104A, the first carrier 616, and the second carrier 618 are coupled together via a coupling mechanism 620, such as a bolt. The first carrier 616 includes the first recessed portion 640 and the second carrier 618 includes the second recessed portion 652. The recessed portions 640, 652 are adjacent one another at the contiguous first end 626 of the first carrier 616 and first end 630 of the second carrier 618. Within the recessed portions 640, 652 are disposed the compression ring 648 and a spring 668. As the combustion engine 100 of FIG. 1 is engaged, combustion products are directed away from combustion chambers to the surrounding environment via their respective cylinders in fluid communication with the manifold segments 104 of the exhaust manifold assembly 112, 500, 600, 700. The assembly 112, 500, 600, 700 disclosed herein each are configured to minimize, for example prevent, leakage of exhaust gases from connections between adjacent manifold segments 104.

With respect to FIG. 6, as the engine heats upon engagement and cools as it is disengaged, thermal expansion and contraction of the assembly 600 may occur. The compression ring 648 and the adjacent spring 668 may cooperate to provide a sustained elastic restoring force at the connection of the manifold segments 104, for example the first manifold segment 104A and the second manifold segment 104B, in radial and axial directions. The sustained force may establish a seal thereby preventing the release of exhaust outside of the segmented manifold assembly 102.

While aspects of the present disclosure have been particularly shown and described with reference to the embodiments above, it will be understood by those skilled in the art that various additional embodiments may be contemplated by the modification of the disclosed machines, systems and methods without departing from the spirit and scope of what is disclosed. Such embodiments should be understood to fall within the scope of the present disclosure as determined based upon the claims and any equivalents thereof. 

We claim:
 1. A composite exhaust manifold assembly comprising: a first manifold segment having a first fluid conduit formed therein and having a flange at a first end thereof; a first carrier disposed adjacent the flange, the first carrier defining at least a portion of a first internal surface, a first recessed portion disposed adjacent the first carrier; a second manifold segment having a second fluid conduit formed therein, the second manifold segment disposed adjacent the first internal surface; and a compression ring disposed adjacent the first recessed portion, the compression ring comprising an outer shell having a mesh core disposed within the shell.
 2. The composite exhaust manifold assembly of claim 1, further comprising a second carrier disposed between the first carrier and the first manifold segment, wherein a first end of the first carrier abuts a first end of the second carrier, wherein at least a portion of the first carrier and the second carrier define the first internal surface, and wherein one of the first end of the first carrier and the first end of the second carrier comprises the first recessed portion.
 3. The composite exhaust manifold assembly of claim 1, wherein the outer shell comprises a split housing with a first portion coupled to a second portion.
 4. The composite exhaust manifold assembly of claim 1, wherein the first carrier is integrated with the flange or coupled thereto.
 5. A composite exhaust manifold assembly comprising: a first manifold segment having a first fluid conduit formed therein and having a flange disposed at a first end of the first manifold segment; a first carrier coupled to the flange, wherein the first carrier defines at least a portion of a first recess and a portion of a second recess; a first compression ring disposed adjacent the first recess; a second compression ring disposed adjacent the second recess, wherein the second compression ring has a concave curvature or concave polygonal cross-section, wherein an interior angle is oriented towards the first compression ring; and a second manifold segment having a second fluid conduit formed therein, the second manifold disposed adjacent an internal surface of the first carrier, wherein the first and second compression rings provide sealing engagement between the second manifold and the first carrier.
 6. The composite exhaust manifold assembly of claim 5, further comprising a second carrier disposed between the first carrier and the flange, wherein the second manifold segment is disposed adjacent an internal surface of the second carrier.
 7. The composite exhaust manifold assembly of claim 6, wherein the second carrier defines at least a portion of the first recess.
 8. The composite exhaust manifold assembly of claim 5, further comprising a retainer disposed adjacent the second recess, wherein the second compression ring is interposed between the retainer and a portion of the first carrier.
 9. The composite exhaust manifold assembly of claim 8, wherein the retainer has an annular shape and is configured to circumscribe an outer periphery of the second manifold segment.
 10. The composite exhaust manifold assembly of claim 5, wherein the first compression ring comprises an outer shell having a mesh core disposed within the shell.
 11. The composite exhaust manifold assembly of claim 10, wherein the outer shell comprises a split housing with a first portion coupled to a second portion.
 12. The composite exhaust manifold assembly of claim 5, wherein the first compression ring comprises a woven wire mesh having a high temperature filler.
 13. The composite exhaust manifold assembly of claim 5, wherein the first recess has an annular shape and a rectangular cross-section.
 14. A composite exhaust manifold assembly comprising: a first manifold segment having a first fluid conduit formed therein and having a flange disposed at a first end of the first manifold segment; a first carrier coupled to the flange, the first carrier having a first end; a first recessed portion formed in the first end of the first carrier; a spring element disposed adjacent the first recessed portion; a compression ring disposed adjacent the spring element; and a second manifold segment having a second fluid conduit formed therein, the second manifold segment disposed adjacent an internal surface of the first carrier, wherein the spring biases the compression ring to provide sealing engagement between the second manifold segment and the first carrier.
 15. The composite exhaust manifold assembly of claim 14, further comprising a second carrier disposed between the first carrier and the flange, wherein the second manifold segment is disposed adjacent an internal surface of the second carrier.
 16. The composite exhaust manifold assembly of claim 14, wherein the compression ring has a polygonal cross-section such as a triangular, trapezoidal, or pentagonal cross-section.
 17. The composite exhaust manifold assembly of claim 14, wherein the compression ring comprises a woven wire mesh comprising a high temperature filler.
 18. The composite exhaust manifold assembly of claim 14, wherein the spring element comprises a conical spring washer in series.
 19. The composite exhaust manifold assembly of claim 14, wherein the second manifold segment further comprises a shoulder spaced from a second end thereof, wherein the shoulder abuts one or more of the spring element and the compression ring.
 20. A composite exhaust manifold assembly comprising: a first carrier defining at least a portion of a first internal surface, the first carrier comprising one or more recesses formed in the first internal surface; and one or more compression rings disposed respectively in the one or more recesses wherein the one or more compressions rings comprises a mesh ring, comprises a concave curvature or concave polygonal cross-section, or comprises a biasing spring element. 